NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Numerical solution of transonic wing flows using an Euler/Navier-Stokes zonal approachTransonic flow fields about wing geometries are computed using an Euler/Navier-Stokes approach in which the flow field is divided into several zones. The grid zones immediately adjacent to the wing surface are suitably clustered and solved with the Navier-Stokes equations. Grid zones removed from the wing are less finely clustered and are solved with the Euler equations. Wind tunnel wall effects are easily and accurately modeled with the new grid-zoning algorithm because the wind tunnel grid is constructed as an exact subset of the corresponding free-air grid. Solutions are obtained that are in good agreement with experiment, including cases with significant wind tunnel wall effects and shock-induced separation on the upper wing surface.
Document ID
19850058591
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Holst, T. L.
(NASA Ames Research Center Moffett Field, CA, United States)
Gundy, K. L.
(NASA Ames Research Center Moffett Field, CA, United States)
Thomas, S. D.
(NASA Ames Research Center Moffett Field, CA, United States)
Chaderjian, N. M.
(NASA Ames Research Center Moffett Field, CA, United States)
Flores, J.
(Informatics General Corp. Palo Alto, CA, United States)
Date Acquired
August 12, 2013
Publication Date
July 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 85-1640
Accession Number
85A40742
Funding Number(s)
CONTRACT_GRANT: NCA2-OR-745-309
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available